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Reversible blade damper

a damper and blade technology, applied in the direction of leakage prevention, engine fuction, machines/engines, etc., can solve the problem that the damper has not always been adequately secured

Active Publication Date: 2015-10-06
RTX CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The reversible damper ensures secure mounting and effective vibration dissipation regardless of orientation, maintaining radial reaction surfaces and preventing misalignment issues, thus enhancing the operational stability of gas turbine engines.

Problems solved by technology

The blade pocket which should receive the foot does not, and thus the damper has not always been adequately secured.
However, the prior art damper has sometimes been inadvertently mounted such that it is rotated by 180° from the position shown in FIG. 1C.
This is undesirable.

Method used

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  • Reversible blade damper
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Examples

Experimental program
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Embodiment Construction

[0037]Referring to FIG. 2, a gas turbine engine 10 includes a fan section 12, a compressor section 14, a combustor section 16, and a turbine section 18. Air entering into the fan section 12 is initially compressed and fed to the compressor section 14. In the compressor section 14, the incoming air from the fan section 12 is further compressed and communicated to the combustor section 16. In the combustor section 16, the compressed air is mixed with gas and ignited to generate a hot exhaust stream 28. The hot exhaust stream 28 is expanded through the turbine section 18 to drive the fan section 12 and the compressor section 14. In this example, the gas turbine engine 10 includes an augmenter section 20 where additional fuel can be mixed with the exhaust gasses 28 and ignited to generate additional thrust. The exhaust gasses 28 flow from the turbine section 18 and the augmenter section 20 through an exhaust liner assembly 22.

[0038]Referring to FIG. 3A, a turbine section 18 includes a p...

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PUM

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Abstract

A damper body extends between an axial first end, an opposing axial second end, a first lateral side, and an opposing second lateral side. A first pair of lugs are disposed at the first axial end and a second pair of lugs are disposed at the second axial end. In the first lug pair, a lug has an axially outermost foot which extends laterally beyond a lateral wall. The second lug pair has a lug with an axial outermost point with a foot extending laterally beyond a lateral wall. The foot on the first axial end and the foot on the second axial end are on opposed lateral sides.

Description

STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT[0001]This invention was made with government support under Contract No. N00019-02-3003 awarded by the United States Air Force. The Government has certain rights in this invention.BACKGROUND OF THE INVENTION[0002]This application relates generally to a turbine blade platform seal and damper assembly and specifically to a reversible blade damper within the assembly.[0003]Conventional gas turbine engines include a turbine assembly that has a plurality of turbine blades attached about a circumference of a turbine rotor. Each of the turbine blades is spaced a distance apart from adjacent turbine blades to accommodate movement and expansion during operation. The blades typically include an attachment that attaches to the rotor, a platform that extends between pressure and suction sides, and an airfoil that extends radially outwardly from the platform. There is a gap between adjacent platforms.[0004]A blade platform seal is ut...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): F01D5/26F01D5/22F01D11/00
CPCF01D5/22F01D5/26F01D11/005F01D11/008F01D11/006F05D2260/36
Inventor DONNELL, BRANDON S.GIRMA, YAFETO'DELL, GINA C.
Owner RTX CORP